Date of Award

Fall 2010

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Mechanical & Aerospace Engineering

Program/Concentration

Aerospace Engineering

Committee Director

Osama A. Kandil

Committee Member

Colin Britcher

Committee Member

Robert E. Bartels

Call Number for Print

Special Collections; LD4331.E535 A83 2010

Abstract

The objective of this project is to improve the aerodynamic performance of an aircraft in transonic speed using a two dimensional contour bump. A natural laminar flow airfoil, RAE5243, has been chosen for the validation case to demonstrate the adequacy of the flow solver used in this study. 2D contour bump is parameterized as the bump position via airfoil, the crest position via bump, maximum height and length of the bump for the parametric study. After these studies, one of the gradient based optimization techniques is utilized to optimize the 2D bump parameters to achieve an augmentation in lift-to-drag ratio. It is observed that an effective increase of 2.60% in the lift-to-drag ratio is obtained as a result of the optimization process, In addition to optimization of the bump, oscillation of the bump section over an airfoil is carried out to check for the performance of the airfoil. Results show that there is improvement of 3.03% in the lift-to-drag ratio when the frequency is 0.006.

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DOI

10.25777/19vq-n217

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